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EP0695856B1 - Kompressor-Robotscheibe mit asymmetrischer Umfangsnut - Google Patents

Kompressor-Robotscheibe mit asymmetrischer Umfangsnut Download PDF

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Publication number
EP0695856B1
EP0695856B1 EP95401820A EP95401820A EP0695856B1 EP 0695856 B1 EP0695856 B1 EP 0695856B1 EP 95401820 A EP95401820 A EP 95401820A EP 95401820 A EP95401820 A EP 95401820A EP 0695856 B1 EP0695856 B1 EP 0695856B1
Authority
EP
European Patent Office
Prior art keywords
disc
blade
lip
angle
downstream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP95401820A
Other languages
English (en)
French (fr)
Other versions
EP0695856A1 (de
Inventor
Jacques Marie Pierre Stenneler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0695856A1 publication Critical patent/EP0695856A1/de
Application granted granted Critical
Publication of EP0695856B1 publication Critical patent/EP0695856B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a disc and blade assembly of disc turbomachine compressor having a groove asymmetrical circular designed to receive vanes hammer attachment.
  • GENERAL US-A-4,460,315 ELECTRIC describes a blade root with hammer attachment, mounted on a conical shell with face angles of support ⁇ and ⁇ 'equal but with opposite slopes and with contact surfaces offset radially one by compared to each other.
  • US-A-2,295,012 describes a system for fixing blades where the foot blade has a bearing face on the disc cavity which is parallel to the radial axis of the blade.
  • Document FR-A-2 697 051 describes a blading compressor with pinhole cells in which we increase more or less the material at the periphery of the disc so what compensate for the differences in forces in the socket.
  • connections blade / disc consists of axial fasteners machined at the periphery of the discs to allow the feet of the blades to be there nested.
  • Figure 1A schematically represents, according to a view in perspective, a disc conforming to the latter blade / disc connection design and comprising a symmetrical circular groove into which are inserted the feet of blades with hammer attachment.
  • the disc 1 which has the circular groove 3.
  • This groove 3 has itself an upstream lip 5 and a downstream lip 7.
  • Dawn 2 like all the blades mounted on the disc 1, has a blade root 4 whose shape resembles substantially like a hammer. Hence the name “dawn at hammer attachment ".
  • FIG. 1B the same is shown blade / disc connection as that of FIG. 1A, but according to a front view. So we see on this figure 1B, blade root 4 of blade 2, groove 3 of the disc 1, as well as the upstream 5 and downstream lips 7.
  • This figure 1B further shows that the blade root 4 has a shape likely to be held in groove 3 while being limited, in motion, by the lips 5 and 7 of the throat 3. These lips 5 and 7 have notches introduction 6 for inserting the blade roots in the throat 3. They also have the role of ensuring maintaining the blade root 4 inside the groove 3 whatever the forces exerted on dawn 2.
  • FIG. 1B further shows that the groove 3 is symmetrical, lips 5 and 7 having curvatures of which the respective slopes P5 and P7 are inclined by the same angle ⁇ relative to a plane P perpendicular to the axis of rotation of the disc.
  • This axis of rotation has not been shown in FIG. 1B for reasons of simplification of this figure; we may however state that it is significantly parallel to the base 2a of dawn 2.
  • angles ⁇ between the slopes P5 and P7 of the curvatures of the lips 5 and 7 and the plane P being equal, we understand that, in this case, the components R1 and R2 of the centrifugal force Fc induced by blade 2 on the lips 5 and 7 of throat 3 (which are also called contact forces on the lips 5 and 7) are symmetrical with respect to the plane P and equal. Strength resulting R from these components R1 and R2 is therefore same direction and same direction as the centrifugal force Fc and their origin points are aligned on the axis disc radial.
  • upstream ferrules and downstream ferrules of the same disc generally have different geometries. most often the upstream shell (shell 9 in FIG. 1B) is conical while the downstream ferrule (ferrule 11 on the Figure 1B) is cylindrical. It therefore follows that the upstream lip 5 and downstream lip 7 of the circular groove 3 are not subject to the same requests.
  • FIGs 2A and 2B there is shown hammerhead blades mounted in disc 1 a conical vein, i.e. an inclined vein as can be found in a double flow motor very high dilution rate.
  • the taper of the vein requires a large gap between positions radial of the bearing faces of the lips 5 and 7, i.e. inner faces at the groove against which the blade root is in support; this gap influences the axial position of the resultant R of components R1 and R2 of the centrifugal force on the lips 5 and 7.
  • This resultant R is then found misalignment of the centrifugal force Fc, which means that the direction and direction of the faces R and Fc are identical but their origins are not aligned on the radial axis of the disc.
  • the reference d, in FIG. 2A, represents the difference between the resultant R and the force centrifugal Fc exerted at the center of gravity of the blade 2. Such misalignment generally produces a torque parasite on dawn 2.
  • FIG. 2A a example of a vein with a taper such as the axis of the component R1 passes close to the bearing face of the downstream lip 7.
  • FIG. 2B the same is shown example of a blade / disc connection as in FIG. 2A, but in the situation where dawn 2 is rotate around the center of rotation C.
  • This figure 2B shows that the blade root 4 can escape out throat 3 of the disc.
  • the object of the present invention is precisely to remedy the drawbacks mentioned above. AT to this end, it offers in a disc and blade assembly a compressor disc of which the circular groove has downstream and upstream lips asymmetrical to each other, the upstream lip having an inclined slope curvature (P5) of an angle ⁇ with respect to this plane (P) perpendicular to the axis of rotation and the downstream lip having a curvature of slope (P7) inclined by an angle ⁇ relative to said plane perpendicular to the axis of rotation, the angle ⁇ being larger than the angle ⁇ and the angles ⁇ and ⁇ being non-zero.
  • P5 inclined slope curvature
  • P7 curvature of slope
  • FIG 3 there is shown, according to a front view, the blade / disc connection in accordance with the invention.
  • a blade 2 whose the blade root 4 is introduced into the circular groove 3 of disc 1.
  • P7 the slope of the curvature of the lip downstream 7; this slope is referenced P7.
  • P5 the slope of the curvature of the upstream lip 5; this slope bears the reference P5.
  • the slope P7 of the curvature of the lip 7 forms an angle ⁇ with the plane P perpendicular to the axis of rotation of the disc, this axis of rotation not having been shown for the reasons given above during the description of Figure 1B.
  • the right representing the slope P5 of the curvature of the lip upstream 5 forms an angle ⁇ with the plane P.
  • the angle ⁇ is strictly different from the angle ⁇ .
  • the angle ⁇ is greater than the angle ⁇ , the angles ⁇ and ⁇ being non-zero.
  • the angle ⁇ between the plane P and the bearing face of the lip 7 is smaller than the angle ⁇ between the plane P and the bearing face of the upstream lip 5.
  • This arrangement of the orientations slopes P5 and P7 causes contact forces due to the centrifugal effect R1 and R2 different.
  • the contact force R2 due to the centrifugal force on the bearing face of the lip 7, is strictly lower than the contact force R1 due to the centrifugal force on the bearing face of the lip 5.
  • the resultant R of these contact forces R1 and R2 is moved downstream of the disc.
  • the axial blade / disc arrangement is therefore different from the arrangement described in the prior art (FIG. 1B).
  • blade / disc links in which the groove 3 of the disc is asymmetrical allows to facilitate the mounting of the blade in the disc by preventing the mounting of the blade "upside down", since one of the lips of the throat 3 has a more curvature important than the other.
  • FIG. 4A a blade / disc connection in accordance with the invention and applied to a strongly inclined vein.
  • This vein is similar to that shown in Figure 2A showing a prior art blade / disc connection in a strongly inclined vein.
  • FIG. 4A a part of the disc 1 has been represented with its circular groove 3. Due to the inclination of the vein, we can notice that, as in figure 2A, the blade root 4 has a shape substantially different from the shape of the blade root 4, shown in FIG. 1B or in Figure 3. This is explained by the fact of the significant inclination of the vein. Nevertheless, such blade roots 4 are also part of the type hammer-attached blades, since the shape of this foot dawn looks almost like a hammer.
  • FIG. 4A it can also be seen that the blade root 4 rests, on the one hand, on the face of support of the upstream lip 5 and, on the other hand, on the bearing face of the downstream lip 7.
  • P5 the slope of curvature of the lip upstream 5 and P7 the curvature slope of the downstream lip 7.
  • the contact forces R1 and R2 are therefore perpendicular, respectively, to these slopes P5 and P7.
  • the result of these contact forces R1 and R2 is referenced R.
  • the slope P5 forms with the plane P perpendicular to the axis of rotation of the disc 1, a angle referenced ⁇ .
  • the slope P7 of the downstream lip 7 forms with this same plane P an angle ⁇ .
  • the angle ⁇ between the slot P5 of the upstream lip 5 and the plane P is strictly greater than the angle ⁇ between the slope P7 of the lip downstream 7 and plane P.
  • a difference in value of the angles ⁇ and ⁇ allows to obtain different mechanical stresses on either side of the throat 3, that is to say around the upstream lip 7 and the downstream lip 5.
  • the choice of an angle ⁇ greater than the angle ⁇ , from art anterior, itself greater than the angle ⁇ allows, in taking into account the contact forces R1 and R2 and the forces transmitted by the ferrules F1 and F2, to obtain a substantially equivalent or even equal lifespan, for the upstream side of the circular groove 3 and the side downstream of this gorge.
  • Figure 4B the same is shown blade / disk connection as in FIG. 4A, but in the case where the blade 2, subjected to axial stresses important, pivots around the center of rotation C, formed by the end of the downstream lip 7. If one compare this figure 4B to figure 2B of the art it is easy to understand the advantage of choosing an angle ⁇ greater than the angle ⁇ of the prior art, this which corresponds to choosing an upstream lip 5 of curvature stronger than that of the prior art. In parallel, the choice of an angle ⁇ less than the angle ⁇ of the FIG. 2B amounts to choosing a downstream lip 7 having a lower curvature than art prior.
  • such a blade / disc link provided an asymmetrical cylindrical groove 3 between the side upstream and the downstream side of the disc 1, has the advantage, on the one hand, to allow obtaining a lifetime parts downstream and parts upstream of the disc substantially equivalent, or even equal and, on the other hand, to obtain an alignment of the centrifugal force Fc from dawn with the resultant R of the contact forces blades in the throat of the disc, which prevents the creation of parasitic couples.
  • this dawn / disc connection provides an improvement, for highly inclined vein compressors, resistance to tearing of blades subjected to significant axial stresses.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

  1. Scheibe/Schaufeln-Gesamtanordnung eines Turbomaschinen-Kompressors, bestehend aus einer Scheibe, die Rotationsbewegungen um eine Rotationsachse ausführen kann und an ihrem Umfang eine umlaufende Nut (3) aufweist, in denen im wesentlichen hammerförmige Schaufelfüsse (4) Aufnahme finden, wobei die genannte Umfangsnut eine vordere Lippe (5) und eine hintere Lippe (7) aufweist, an denen sich die Schaufelfüsse in Anlage befinden, wobei die vordere Lippe und die hintere Lippe der Umfangsnut, bezogen auf eine senkrechte Ebene (P) zur Rotationsachse, asymmetrisch sind, indem die vordere Lippe eine Neigungskrümmung (P5) aufweist, die um einen Winkel α zu dieser senkrechten Ebene (P) zur Rotationsachse geneigt ist, und die hintere Lippe eine Neigungskrümmung (P7) aufweist, die um einen Winkel β zu dieser senkrechten Ebene (P) zur Rotationsachse geneigt ist, wobei der Winkel α größer ist als der Winkel β und die Winkel α und β ungleich Null sind.
  2. Scheibe/Schaufeln-Gesamtanordnung eines Turbomaschinen-Kompressors nach Anspruch 1,
       dadurch gekennzeichnet, daß die aufgrund der Zentrifugalkräfte von der Schaufel auf die vordere Lippe (5) und die hintere Lippe (7) ausgeübten Berührungskräfte R1 bzw. R2 so beschaffen sind, daß R1 größer ist als R2 und die Resultierende R dieser Kräfte R1 und R2 so beschaffen ist, daß die Resultierende zur hinteren Seite der Scheibe hin verschoben wird.
EP95401820A 1994-08-03 1995-08-03 Kompressor-Robotscheibe mit asymmetrischer Umfangsnut Expired - Lifetime EP0695856B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9409595 1994-08-03
FR9409595A FR2723397B1 (fr) 1994-08-03 1994-08-03 Disque de compresseur de turbomachine muni d'une gorge circulaire asymetrique

Publications (2)

Publication Number Publication Date
EP0695856A1 EP0695856A1 (de) 1996-02-07
EP0695856B1 true EP0695856B1 (de) 1999-04-14

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ID=9466006

Family Applications (1)

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EP95401820A Expired - Lifetime EP0695856B1 (de) 1994-08-03 1995-08-03 Kompressor-Robotscheibe mit asymmetrischer Umfangsnut

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US (1) US5584658A (de)
EP (1) EP0695856B1 (de)
DE (1) DE69509015T2 (de)
FR (1) FR2723397B1 (de)

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GB9606963D0 (en) * 1996-04-02 1996-06-05 Rolls Royce Plc A root attachment for a turbomachine blade
DE19654471B4 (de) * 1996-12-27 2006-05-24 Alstom Rotor einer Strömungsmaschine
GB2364554B (en) * 2000-07-07 2004-04-07 Alstom Power Nv Turbine disc
FR2857405B1 (fr) * 2003-07-07 2005-09-30 Snecma Moteurs Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique
FR2861128B1 (fr) * 2003-10-16 2007-06-08 Snecma Moteurs Dispositif d'attache d'une aube mobile sur un disque de rotor de turbine dans un turbomachine
DE102004051116A1 (de) * 2004-10-20 2006-04-27 Mtu Aero Engines Gmbh Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
FR2886336B1 (fr) * 2005-05-26 2007-08-24 Snecma Moteurs Sa Perfectionnement a une roue aubagee de rotor pour renforcer le verrouillage des aubes
EP1801355B1 (de) * 2005-12-23 2015-02-11 Techspace Aero Laufschaufelschloss für eine Turbomaschinenrotorscheibe
DE102007035680B4 (de) * 2007-07-30 2016-02-04 Mbda Deutschland Gmbh Täuschsystem für Satellitennavigationssysteme
US20100166561A1 (en) * 2008-12-30 2010-07-01 General Electric Company Turbine blade root configurations
US8251667B2 (en) 2009-05-20 2012-08-28 General Electric Company Low stress circumferential dovetail attachment for rotor blades
DE102009030397A1 (de) * 2009-06-25 2010-12-30 Mtu Aero Engines Gmbh Befestigungsvorrichtung einer Turbinen- oder Verdichterschaufel
US8651820B2 (en) * 2010-07-14 2014-02-18 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
US8734112B2 (en) 2010-11-30 2014-05-27 United Technologies Corporation Asymmetrical rotor blade slot attachment
FR2968363B1 (fr) * 2010-12-03 2014-12-05 Snecma Rotor de turbomachine avec une cale anti-usure entre un disque et un anneau
US9127555B2 (en) * 2010-12-21 2015-09-08 Solar Turbines Incorporated Method for balancing rotating assembly of gas turbine engine
US8932023B2 (en) * 2012-01-13 2015-01-13 General Electric Company Rotor wheel for a turbomachine
CN102588003B (zh) * 2012-03-15 2014-12-24 北京航空航天大学 一种低应力双圆弧面直榫连接结构
US9068465B2 (en) 2012-04-30 2015-06-30 General Electric Company Turbine assembly
GB201416505D0 (en) * 2014-09-18 2014-11-05 Rolls Royce Plc Gas turbine engine
GB201502612D0 (en) * 2015-02-17 2015-04-01 Rolls Royce Plc Rotor disc

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US2295012A (en) * 1941-03-08 1942-09-08 Westinghouse Electric & Mfg Co Turbine blading
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DE4324960A1 (de) * 1993-07-24 1995-01-26 Mtu Muenchen Gmbh Laufrad einer Turbomaschine, insbesondere einer Turbine eines Gasturbinentriebwerks

Also Published As

Publication number Publication date
DE69509015T2 (de) 1999-10-07
FR2723397A1 (fr) 1996-02-09
DE69509015D1 (de) 1999-05-20
FR2723397B1 (fr) 1996-09-13
EP0695856A1 (de) 1996-02-07
US5584658A (en) 1996-12-17

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